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Gas compressor circumferential direction vorticity through-flow design method

A design method and compressor technology, applied in mechanical equipment, machines/engines, liquid fuel engines, etc., can solve problems such as high experience requirements, vorticity field guiding circulation distribution, etc.

Active Publication Date: 2009-11-04
北京飞擎科技有限公司
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AI Technical Summary

Problems solved by technology

The traditional through-flow design method has high requirements for the designer’s experience, and has not yet guided the distribution of circulation from the perspective of rationally organizing the vorticity field

Method used

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  • Gas compressor circumferential direction vorticity through-flow design method
  • Gas compressor circumferential direction vorticity through-flow design method
  • Gas compressor circumferential direction vorticity through-flow design method

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Embodiment Construction

[0028] The specific implementation method of the compressor circumferential vortex flow design method of the present invention is as follows figure 1 shown, including:

[0029] Step 1. Given the geometric data such as flow channel curves and blade leading and trailing edge curves required by the flow design, generate meridian surface calculation grids, and give the initial aerodynamic design parameter circulation distribution, including radial and axial Distribution form, use the through-flow program to calculate the meridian surface flow field;

[0030] Step 2. According to the definition of vorticity, the vorticity field is solved by the velocity field, and the distribution of the circumferential vorticity on the meridian plane is obtained;

[0031] Step 3. Determine whether the obtained circumferential vorticity distribution meets the requirements according to the optimal distribution criterion of the circumferential vorticity, that is, check whether the positive and negat...

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Abstract

The invention relates to a circumferential direction vorticity through-flow design method of an aero-engine gas compressor. The circumferential direction vorticity distribution has a significant influent on the overall performance of the gas compressor and acts as critical diagnostic parameters of vorticity dynamics; in the through-flow design stage, the important design parameter circulation distribution is optimized so as to control the circumferential direction vorticity in advance and realize the design of the gas compressor with high performance. The method obtains a circulation optimal iterative formula according to the optimal distribution criterion of the circumferential direction vorticity close to zero in the main flow area of a meridian plane and the close relation of the vorticity and the circulation on the basis of a Crocco equation, can conveniently and automatically optimize the circulation distribution from the initial circulation distribution, realizes the better distribution of the circumferential direction vorticity, increases the pressure ratio and efficiency of the gas compressor, and guides the air-powered design of the gas compressor.

Description

technical field [0001] The invention relates to an aerodynamic design method of an aero-engine compressor, in particular to a design method of the flow of the compressor with the circumferential vortex as a diagnosis parameter. Background technique [0002] The compressor is one of the three major components of an aero-engine, which performs the work of compressing the airflow. The internal flow of the compressor is very complicated, and there are various vortex structures, such as wake vortex, tip leakage vortex, channel vortex, etc. Various vortex structures have a quantitative impact on the overall performance parameters of the compressor, such as pressure ratio and efficiency. The distribution of the field is the key to the success of the compressor design. [0003] The through-flow design method is a necessary step in the preliminary design of the compressor. The through-flow design is to calculate the flow parameters of the meridian plane under the assumption of axis...

Claims

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Application Information

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IPC IPC(8): F04D29/26F04D29/40F04D29/66
Inventor 李秋实李志平吴宏周盛陆亚钧
Owner 北京飞擎科技有限公司
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